Journal of Textile Research ›› 2021, Vol. 42 ›› Issue (07): 108-114.doi: 10.13475/j.fzxb.20200704107

• Textile Engineering • Previous Articles     Next Articles

Free form deformation modeling method and inflation mechanism of folded canopy fabrics

ZHANG Siyu1, YU Li1(), JIA He1,2, LIU Xin1   

  1. 1. Key Laboratory of Aircraft Environment Control and Life Support, MIIT, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210016, China
    2. Beijing Institute of Space Mechanics & Electricity, Beijing 100094, China
  • Received:2020-07-17 Revised:2021-03-10 Online:2021-07-15 Published:2021-07-22
  • Contact: YU Li E-mail:yuli_happy@163.com

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Abstract:

Folded flexible canopy fabrics of ram-air parachutes modeling is a key problem in the interaction calculation during inflation process. According to physical folding characteristics, a modeling method of folded canopy fabrics was proposed based on free form deformation. The wing surface deformation was achieved by moving control nodes with direct constraint method of free form deformation. The spanwise folding was obtained by coordinate matrix transformation. In order to modify the geometric errors, the initial stress method was introduced to make the folded model with mechanical characteristics. The folded canopy fabrics model of a certain ram-air parachute was established using this method, and the fluid-structure interaction calculation was carried out based on the arbitrary Lagrange-Euler method during inflation process. The three-dimensional shape, stress and unsteady flow field distribution were obtained. The corresponding calculation and airdrop experiment verified the rationality and feasibility of this method.

Key words: inflatable flexible fabric, folded canopy fabric, ram-air parachutes, free form deformation, inflation mechanism, fluid-structure interaction, fold modeling

CLC Number: 

  • TS101.8

Tab.1

Parameters of canopy fabrics and cord lines"

名称 厚度/m 横截面积/m2 弹性模量/Pa 密度/ (kg·m-3)
伞衣 0.035 — 4.3×108 533.77
伞绳 — 9.0×10-6 9.7×1010 462.00

Fig.1

General framework"

Fig.2

Deformed area and control nodes"

Fig.3

Section of control nodes"

Fig.4

Principle of initial stress modification"

Fig.5

Actual folded canopy fabrics"

Fig.6

Initial geometric model of canopy"

Fig.7

Control nodes and constraints of upper (a) and lower (b) wings surface"

Fig.8

Projection distortion of upper (a) and lower (b) wings surface"

Fig.9

Deformed cells"

Fig.10

Spanwise folded canopy fabrics"

Fig.11

Variation of opening load"

Fig.12

Evolution of structure and flow field during inflation. (a) Velocity vector contour; (b) Pressure contour"

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